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A realization method of partially reconfigurable aerospace SoC

An implementation method and a technology of dynamic modules, which are applied to general-purpose stored-program computers and architectures with a single central processing unit, can solve problems affecting task completion, system degradation, and low adaptability, and achieve strong real-time performance and improved reliability. , to ensure the effect of continuous operation

Active Publication Date: 2017-07-28
BEIJING INST OF CONTROL ENG
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Problems solved by technology

However, the internal function and structure of the SoC device cannot be changed after the design is finalized, and its adaptability is not high in the face of changing space missions. In addition, when some functions in the SoC fail, the system will lose the corresponding part of the failure. The function of the system will be degraded, which will affect the completion of the task

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  • A realization method of partially reconfigurable aerospace SoC
  • A realization method of partially reconfigurable aerospace SoC
  • A realization method of partially reconfigurable aerospace SoC

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Embodiment Construction

[0030] Below in conjunction with accompanying drawing and specific embodiment the present invention is described in further detail:

[0031] Such as figure 1 Shown is the design flowchart of the partially reconfigurable SOC of the present invention, the present invention supports the realization method of the partially reconfigurable aerospace SoC, which specifically includes the following steps:

[0032] (1) According to the needs of the actual application of the dynamic reconfigurable system, determine the structure of the system-on-chip SOC, determine the interface between the static module and the reconfigurable module, such as figure 2 Shown is a schematic diagram of the system structure of the partially reconfigurable SOC of the present invention, each module in the SoC is divided, the modules that do not need to be reconfigured are defined as static modules, the modules that need to be reconfigured are defined as dynamic modules, and all static modules A static system...

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Abstract

The invention relates to a method for realizing a partly reconfigurable aerospace SoC, by defining a dynamic system and a static system in the SoC, and carrying out different designs on the two systems, the system can be configured on the FPGA during the operation of the system Part of the logic is reconfigured, while the logic function of the unconfigured part does not change, so that the dynamic part can be reconfigured with both software flexibility and hardware efficiency, which can effectively solve the problem that the existing SOC internal functions and structures cannot At the same time, the configuration bit stream can be periodically refreshed through partial reconfiguration technology to prevent single event flipping of the configuration bit stream, improve the reliability and fault tolerance of the SOC, and make the function change of the SOC more flexible.

Description

technical field [0001] The invention relates to a method for realizing an aerospace SoC supporting partial reconfigurability, and belongs to the field of highly reliable SoC design based on partial reconfigurability. Background technique [0002] In recent years, with the rapid development of electronic device miniaturization and low power consumption technology, ASIC-based system-on-chip (SoC) is being widely used in many high-reliability fields. Especially in the field of space applications, the use of SoC can significantly reduce the weight of devices, reduce the size of the system, and improve system performance. However, the internal function and structure of the SoC device cannot be changed after the design is finalized, and its adaptability is not high in the face of changing space missions. In addition, when a part of the function fails in the SoC, the system will lose the corresponding part of the failure. function, system degradation occurs, affecting the completi...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F15/78
Inventor 赵云富孙强施蕾董暘暘胡洪凯叶有时熊军刘波吴一帆
Owner BEIJING INST OF CONTROL ENG
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